Exploration of a turbojet

Single-flow turbofan, compression ratio 20, turbine inlet temperature 1200 °C

Introduction

turbojet

A turbojet engine of the type generally used in aviation is a simple modification of an open cycle gas turbine studied previously: the turbine is sized to only drive the turbochcompressor.

At the turbine outlet, the excess energy available in the gases at high pressure and temperature is converted into kinetic energy in a nozzle.

The thrust results from the difference of momentum between intake and exhaust gases.

The turbojet also includes an inlet diffuser, which is used to create a static precompression at the compressor inlet.

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A turbojet is therefore the combination of a diffuser, a gas generator and a nozzle.

We speak of a gas generator because the function of the "compressor, combustion chamber and turbine" assembly is to generate hot gases at a pressure higher than ambient pressure, so that these gases can then be converted in kinetic energy into the nozzle.

It is quite possible to model with good precision various cycles of turbojets with Thermoptim.

However, Thermoptim core components are not sufficient to build such models: to represent the inlet diffuser and the exit nozzle, it is here necessary to use two external classes, i.e. two extensions of the software.

In this guided exploration, we will study the cycle of a single-flow turbojet engine..